Abstract: A rotary engine rotor and a method for supplying rotary engine rotors are provided. The rotary engine rotor has a center axis, a rotor body, a plurality of peripheral surfaces, and a plurality of recess members. The rotor body has a central bore that extends along the center axis. The plurality of peripheral surfaces are disposed around an exterior perimeter of the rotor body. Each of the plurality of recess members are disposed in a respective one of the plurality of peripheral surfaces. Each recess member includes an interior cavity open to an exterior of the rotor.

Abstract: A multi-engine aircraft includes first and second gas turbine engines for providing motive power to the aircraft, each of the first and second engines comprising an air system, an air pressure line extending between and fluidly connecting the air systems of the first and second engines, and a pressure wave damper communicating with the air pressure line extending between the first and second engines.

Abstract: A method of reducing noise includes: driving a first propulsor using one or more of the first electrical motor and the first thermal engine, and driving a second propulsor of the second hybrid power plant using one or more of the second electrical motor and the second thermal engine; receiving a signal indicative of an initial combined noise signature; determining, from the signal, that an initial amplitude variation of a periodically fluctuating amplitude of the initial combined noise signature is greater than an amplitude variation threshold; modulating a thrust produced by the second hybrid power plant, by changing a power output of the second thermal engine or the second electrical motor, to produce a modulated combined noise signature having a modulated amplitude variation less than the initial amplitude variation; and compensating for a difference in thrusts generated by the first hybrid power plant and the second hybrid power plant.

Abstract: A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.

Abstract: A method and a system for synthesizing thrust from a turbofan engine are provided. The turbofan engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine, a pressure of fluid at an exit of the compressor section and a temperature of fluid at a location upstream of the exit of the compressor section are determined. A synthesized value of thrust from the turbofan engine is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine is output.

Abstract: A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.

Abstract: A method and a system for synthesizing thrust from a turbofan engine are provided. The turbofan engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine, a pressure of fluid at an exit of the compressor section and a temperature of fluid at a location upstream of the exit of the compressor section are determined. A synthesized value of thrust from the turbofan engine is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine is output.

Abstract: A system has: a combustor; a plenum surrounding the combustor; a transfer tube having an inlet fluidly connected to the plenum and at least two outlets, a first flow passageway defined between the inlet and a first outlet, a second flow passageway defined between the inlet and a second outlet, the second flow passageway connected to a discharge region outside of the plenum; a flow valve disposed within the second flow passageway and operable between an open position and a closed position, in the open position the flow valve fluidly connects the plenum with the discharge region, in the closed position the flow valve blocking fluid communication between the plenum and the discharge region; and a controller communicatively coupled to the flow valve to control operation thereof by: causing the flow valve to open for a time period; and subsequent to the time period, causing the flow valve to close.

Abstract: There is described a method of operating a gas turbine engine having a rotor rotatable about a rotation axis, a core gas path defined annularly around the rotation axis, and a casing defining a wall to the core gas path. The method generally has: generating compressed air from a compressed air source, the compressed air source being external relative the gas turbine engine; and guiding the compressed air in sequence from the compressed air source, radially inwardly relative the rotation axis, through a bleed port and into the core gas path.

Abstract: The exhaust mixer can have a conduit extending around a central axis, and along the axis to a trailing edge, the conduit extending between a radially-outer bypass path and a radially-inner core gas path, the conduit having a plurality of apertures spaced-apart from one another around the circumference of the conduit and fluidly connecting the bypass path to the core gas path upstream of the trailing edge.

Abstract: Sandwich-structured noise-attenuating and/or structural panels and methods of manufacturing such panels using ultrasonic welding are described. The method includes: receiving a backing member, a sheet and a cellular structure; assembling the cellular structure between the backing member and the sheet; and ultrasonically welding the backing member and the sheet together.

Abstract: A system has: a combustor; a plenum surrounding the combustor; a transfer tube having an inlet fluidly connected to the plenum and at least two outlets, a first flow passageway defined between the inlet and a first outlet, a second flow passageway defined between the inlet and a second outlet, the second flow passageway connected to a discharge region outside of the plenum; a flow valve disposed within the second flow passageway and operable between an open position and a closed position, in the open position the flow valve fluidly connects the plenum with the discharge region, in the closed position the flow valve blocking fluid communication between the plenum and the discharge region; and a controller communicatively coupled to the flow valve to control operation thereof by: causing the flow valve to open for a time period; and subsequent to the time period, causing the flow valve to close.

Abstract: A method for operating a gas turbine engine comprises providing fuel flow and compressed airflow to a combustor with a fuel-to-air ratio, the compressed airflow being from a compressed air source; detecting at least one parameter indicative of the fuel-to-air ratio being below a predetermined value; and bleeding compressed air from the compressed air source when the at least one parameter indicative of the fuel-to-air ratio is below the predetermined value to increase the fuel-to-air ratio to at least the predetermined value.

Abstract: An aircraft component and an associated method of manufacturing such aircraft component are disclosed. The aircraft component comprises a backing member, a porous sheet spaced apart from the backing member, and a cellular structure disposed between the backing member and the porous sheet. The cellular structure is attached to at least one of the backing member and the porous sheet by one or more non-adhesive connections.

Abstract: The gas turbine engine includes a fluid system fluidly connecting at least two components of the gas turbine engine, and a tunable resonator in fluid flow communication with the fluid system. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.

Abstract: A fluid system of an aircraft engine includes a first and second fluid conduits. The first conduit fluid conduit fluidly connects to the aircraft engine. A pump fluidly connects to the first fluid conduit and moves therethrough a fluid imparting an excitation frequency to the fluid. The second fluid conduit fluidly connects to the first fluid conduit and to a pressure sensor. A weight is disposed in the second fluid conduit and movable between a first and second positions. A mass of the weight and a liquid capacitance of the second fluid conduit between the second position and a second end of the second fluid conduit define a resonance frequency that is less than the excitation frequency. Fluid pressure monitoring and pressure noise filter construction methods are also disclosed.

Abstract: A multi-engine aircraft includes first and second gas turbine engines for providing motive power to the aircraft, each of the first and second engines comprising an air system, an air pressure line extending between and fluidly connecting the air systems of the first and second engines, and a pressure wave damper communicating with the air pressure line extending between the first and second engines.

Abstract: Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.

Abstract: A bleed air system is disclosed for a turbofan engine having a bypass duct. The bleed air system includes a bleed air conduit having an inlet end connected to the bypass duct and a bleed air flow control valve disposed downstream of the inlet end, and a louver assembly disposed within the opening at inlet end of the bleed air conduit. The louver assembly includes an airfoil-shaped louver blade which extends across the opening in a direction transverse to the flow direction within the bypass duct. A reinforcing rib is attached to the louver blade and extends across the louver assembly in a direction generally parallel to the flow direction.

Abstract: Herein provided are methods and systems for reducing an acoustic signature of a gas turbine engine. An acceleration command for the engine is received. In response to receiving the acceleration command: a fuel flow to the engine is increased for a first predetermined time period; subsequent to the first predetermined time period, the fuel flow to the engine is reduced for a second predetermined time period; and subsequent to the second predetermined time period, the fuel flow to the engine is increased for a third time period.